An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

An integrated single stage ac-dc driver for powering LED loads includes a boost converter operating in a Discontinuous Conduction Mode, DCM, comprising a half-bridge, and a Zeta Asymmetrical Half Bridge, ZAHB, integrated with the boost converter such that the boost converter and the ZAHB share the half-bridge to perform power factor control, PFC, with a fixed duty cycle and control an output voltage.

Disclosed is a direct current power supply. The direct current power supply includes a voltage output defining a voltage rail and a ground. The direct current power supply includes a holdup capacitor operable to conduct with the voltage output. The direct current power supply includes a redundant power supply connected in series with the holdup capacitor between the voltage rail and the ground of the voltage output to provide the voltage output. The direct current power supply includes a first switch disposed between the holdup capacitor and the redundant power supply operable to create a conductive path between the holdup capacitor and the redundant power supply.

Disclosed is a direct current power supply. The direct current power supply includes a voltage output defining a voltage rail and a ground. The direct current power supply includes a holdup capacitor operable to conduct with the voltage output. The direct current power supply includes a redundant power supply connected in series with the holdup capacitor between the voltage rail and the ground of the voltage output to provide the voltage output. The direct current power supply includes a first switch disposed between the holdup capacitor and the redundant power supply operable to create a conductive path between the holdup capacitor and the redundant power supply.

An auxiliary power unit, in particular for an aircraft, includes a gas generator and an electric generator. The electric generator has an input shaft that is connected to an output shaft of the gas generator. The auxiliary power unit also has an accessories housing directly connected to a rotor shaft of the electric generator, wherein the electric generator is interposed between the gas generator and the accessories housing.

An auxiliary power unit, in particular for an aircraft, includes a gas generator and an electric generator. The electric generator has an input shaft that is connected to an output shaft of the gas generator. The auxiliary power unit also has an accessories housing directly connected to a rotor shaft of the electric generator, wherein the electric generator is interposed between the gas generator and the accessories housing.

The lifting, stabilizing and propelling arrangement for vertical take-off and landing aircraft, uses rotating wings, turbines or lift fans, propellers and stabilizers on the trailing edges of the wings and empennages, centrifugal or tangential turbines applied on the sides of the fuselage, on the inlet and outlet edges of the wings, or centrifugal or tangential turbines on the sides of the fuselage and inside the wings, those that carry the fuselage are fixed and produce only lift and those that go in the wings they rotate with them and produce lift during vertical flight and propulsion during horizontal flight, add some horizontal stabilizing fans at the tips of the wings and others for direction in the vertical empennage.

A method for measuring the hardware and operational state of a dual-circuit solenoid valve including first and second coaxial coils each associated with a circuit is disclosed. The method includes the steps of injecting a sinusoidal current into the first coil; measuring the voltage induced across the terminals of the second coil; and plotting at least one curve of a first magnitude proportional to the measured induced voltage as a function of a second magnitude proportional to the injected sinusoidal current.

There is disclosed in one example an apparatus, including: a hardware platform including a processor and a memory; and instructions encoded within the memory to instruct the processor to: receive stored performance data for an aircraft battery, the stored performance data including data that correlate power density to temperature and remaining charge; simulate a planned flight for an aircraft, including predicting a plurality of temperature and remaining charge values; and direct operation of a heat exchange apparatus to precondition the battery to a selected temperature before the planned flight.